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There is no current sustainable, moderate temperature thermal solution for global lunar access. Lunar equatorial temperatures may exceed 250 deg F. Apollo missions boiled consumable H2O for heat rejection and avoided the hottest part of the lunar day. The NASA Surveyor missions utilized specialized high temperature avionics. The proposed innovation would provide indefinite, sustainable heat rejection for global lunar surface assets while enabling commercial markets for global lunar access. To allow heat rejection from an advanced thermal radiator, the proposed innovation would incorporate an infrared transparent cover over a semi-transparent absorber to reflect high incident angle radiation originating from surrounding lunar terrain. The technical objective of this effort is to design, build and test a subscale Proof-of-Concept (POC) radiator to advance the technology. Final products would include a radiator design concept and conceptual hardware with anticipated NTR submissions. Industry and government solutions have focused on heat pumps, consumables and increased temperature heat rejection.
The proposed innovation would be considered revolutionary as new technology is incorporated into an existing process for spacecraft/vehicle heat rejection. It is anticipated that the innovation would lead to a patent or NTR application.
Listed on TechPort itself — the most direct way to ask about this specific project.
This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.
None of these are guaranteed paths for this specific project — TechPort itself doesn't have an "apply" button. Reaching out to the contact(s) above with a specific question is usually the fastest way to find out what's actually open.